Title :
An attitude determination method based on UKF and Optimal REQUEST double filter
Author :
Huimin, Zhong ; Wenyong, Yu
Author_Institution :
Dept. of Syst. Overall, China Centre for Resources Satellite Data & Applic., Beijing, China
Abstract :
The Inertial Stellar Compass (ISC) attitude determination system, which is the combination of MEMS (Micro electromechanical Systems) gyros and CMOS APS star sensor, has low precision. Quaternion attitude estimate of UKF has higher attitude estimate precision, and it can also estimate gyro drift, but it needs high precision of attitude parameters as observes. Optimal REQUEST could deal with starlit vectors orderly and giving high precise of attitude parameters. For the mutual complement of two methods, the paper gets attitude parameters from Optimal REQUEST as observes to UKF and puts forward an attitude determination method based on UKF and Optimal REQUEST double filter. The results of simulation show that this method has higher precise of attitude estimate than EKF and Optimal REQUEST filter.
Keywords :
CMOS image sensors; Kalman filters; aerospace control; attitude control; compasses; gyroscopes; microsensors; recursive estimation; CMOS APS star sensor; EKF; ISC attitude determination system; MEMS gyros; UKF quaternion attitude estimation; gyro drift estimation; inertial stellar compass attitude determination system; microelectromechanical system gyros; optimal REQUEST double filter; recursive quaternion estimation; starlit vectors; unscented Kalman filter; CMOS integrated circuits; Compass; Estimation; Heuristic algorithms; Micromechanical devices; Position measurement; Space vehicles; Attitude determination; Dual filter; Optimal REQUEST; The Inertial Stellar Compass; UKF;
Conference_Titel :
Artificial Intelligence, Management Science and Electronic Commerce (AIMSEC), 2011 2nd International Conference on
Conference_Location :
Deng Leng
Print_ISBN :
978-1-4577-0535-9
DOI :
10.1109/AIMSEC.2011.6009809
